Fuel Nozzle Assembly with Inlet Flow Conditioner

ABSTRACT

A combustor includes an inlet flow conditioner having a sleeve and a conditioner plate. The conditioner plate defines a plurality of apertures. The sleeve extends axially from the conditioner plate to a forward plate of a nozzle segment. The sleeve, the conditioner plate and the forward plate define an inlet flow plenum. The inlet flow plenum is in fluid communication with an inlet of a tube that defines a premix passage of the nozzle segment.

FIELD OF THE TECHNOLOGY

The present invention generally involves a combustor for a gas turbine. More specifically, the invention relates to a system for mitigating non-uniform flow upstream from an inlet to a premix passage of a fuel nozzle.

BACKGROUND

During operation of a gas turbine engine, pressurized air from a compressor flows into a head end volume defined within the combustor. The pressurized air flows from the head end volume into an inlet to a corresponding premix passage of a respective fuel nozzle. Fuel is injected into the flow of pressurized air within the premix passage where it mixes with the pressurized air so as to provide a fuel and air mixture to a combustion zone or chamber defined downstream from the fuel nozzle. The flow of pressurized air is typically non-uniform as it approaches the inlet to the respective fuel nozzle which may be undesirable for efficient combustor operations.

BRIEF DESCRIPTION OF THE TECHNOLOGY

Aspects and advantages are set forth below in the following description, or may be obvious from the description, or may be learned through practice.

One embodiment of the present disclosure is a combustor. The combustor includes an inlet flow conditioner having a sleeve and a conditioner plate. The conditioner plate defines a plurality of apertures. The sleeve extends axially from the conditioner plate to a forward plate of a nozzle segment. The sleeve, the conditioner plate and the forward plate define an inlet flow plenum. The inlet flow plenum is in fluid communication with an inlet of a tube that defines a premix passage of the nozzle segment.

Another embodiment of the present disclosure is a combustor. The combustor includes an inlet flow conditioner including a sleeve and a conditioner plate. The conditioner plate defines a plurality of apertures. The sleeve extends axially from the conditioner plate to a forward plate of a fuel nozzle and forms an inlet flow plenum therein. The inlet flow plenum is in fluid communication with a plurality of premix passages which is defined by a plurality of tubes of the fuel nozzle.

Those of ordinary skill in the art will better appreciate the features and aspects of such embodiments, and others, upon review of the specification.

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of the of various embodiments, including the best mode thereof to one skilled in the art, is set forth more particularly in the remainder of the specification, including reference to the accompanying figures, in which:

FIG. 1 is a functional block diagram of an exemplary gas turbine that may incorporate various embodiments of the present disclosure;

FIG. 2 is a simplified cross-section side view of an exemplary combustor as may incorporate various embodiments of the present disclosure;

FIG. 3 is an upstream view of an exemplary fuel nozzle assembly according to at least one embodiment of the present disclosure;

FIG. 4 is a cross-sectioned perspective view of an exemplary nozzle segment according to at least one embodiment of the present disclosure;

FIG. 5 is a perspective view of an exemplary conditioner plate according to at least one embodiment of the present disclosure;

FIG. 6 is a cross-sectioned perspective view of an exemplary fuel nozzle according to at least one embodiment of the present disclosure; and

FIG. 7 is a perspective view of an exemplary conditioner plate according to at least one embodiment of the present disclosure.

DETAILED DESCRIPTION

Reference will now be made in detail to present embodiments of the disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the disclosure.

As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. The terms “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows. The term “radially” refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component, the term “axially” refers to the relative direction that is substantially parallel and/or coaxially aligned to an axial centerline of a particular component, and the term “circumferentially” refers to the relative direction that extends around the axial centerline of a particular component.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.

Each example is provided by way of explanation, not limitation. In fact, it will be apparent to those skilled in the art that modifications and variations can be made without departing from the scope or spirit thereof. For instance, features illustrated or described as part of one embodiment may be used on another embodiment to yield a still further embodiment. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims and their equivalents. Although exemplary embodiments of the present disclosure will be described generally in the context of a combustor for a land based power generating gas turbine for purposes of illustration, one of ordinary skill in the art will readily appreciate that embodiments of the present disclosure may be applied to any style or type of combustor for a turbomachine and are not limited to combustors or combustion systems for land based power generating gas turbines unless specifically recited in the claims.

Referring now to the drawings, FIG. 1 illustrates a schematic diagram of an exemplary gas turbine 10. The gas turbine 10 generally includes a compressor 12, at least one combustor 14 disposed downstream of the compressor 12 and a turbine 16 disposed downstream of the combustor 14. Additionally, the gas turbine 10 may include one or more shafts 18 that couple the compressor 12 to the turbine 16.

During operation, air 20 flows into the compressor 12 where the air 20 is progressively compressed, thus providing compressed or pressurized air 22 to the combustor 14. At least a portion of the compressed air 22 is mixed with a fuel 24 within the combustor 14 and burned to produce combustion gases 26. The combustion gases 26 flow from the combustor 14 into the turbine 16, wherein energy (kinetic and/or thermal) is transferred from the combustion gases 26 to rotor blades (not shown), thus causing shaft 18 to rotate. The mechanical rotational energy may then be used for various purposes such as to power the compressor 12 and/or to generate electricity. The combustion gases 26 may then be exhausted from the gas turbine 10.

As shown in FIG. 2, the combustor 14 may be at least partially surrounded by an outer casing 28 such as a compressor discharge casing. The outer casing 28 may at least partially define a high pressure plenum 30 that at least partially surrounds various components of the combustor 14. The high pressure plenum 30 may be in fluid communication with the compressor 12 (FIG. 1) so as to receive the compressed air 22 therefrom. An endcover 32 may be coupled to the outer casing 28. One or more combustion liners or ducts 34 may at least partially define a combustion chamber or zone 36 for combusting the fuel-air mixture and/or may at least partially define a hot gas path through the combustor 14 for directing the combustion gases 26 towards an inlet 38 to the turbine 16.

In particular embodiments, the combustion liner 34 is at last partially circumferentially surrounded by a flow sleeve 40. The flow sleeve 40 may be formed as a single component or by multiple flow sleeve segments. The flow sleeve 40 is radially spaced from the combustion liner 34 so as to define a flow passage or annular flow passage 42 therebetween. The flow sleeve 40 may define a plurality of inlets or holes 44 which provide for fluid communication between the flow passage 42 and the high pressure plenum 30. In particular embodiments, the endcover 32 and the outer casing 28 at least partially define a head end volume or plenum 46 of the combustor 14. The head end volume 46 may be in fluid communication with the high pressure plenum 30 via the flow passage 42. In various embodiments, as shown in FIG. 2, the combustor 14 includes a fuel nozzle assembly 48.

FIG. 3 provides an upstream view of an exemplary fuel nozzle assembly 48 according to at least one embodiment of the present disclosure. In particular embodiments, as shown in FIG. 3, the fuel nozzle assembly 48 includes a plurality of nozzle segments 100 annularly arranged about a fuel nozzle or center fuel nozzle 200. Although FIG. 3 illustrates four individual nozzle segments 100, the combustor 14 may include two or more nozzle segments 100 and is not limited to four nozzles segments 100 unless otherwise recited in the claims. For example, in an exemplary embodiment, the fuel nozzle assembly 48 may include five nozzle segments annularly arranged around a center fuel nozzle 200. In other embodiments, fuel nozzle assembly 48 may include just a single fuel nozzle 200. As shown in FIG. 2, each of the nozzle segments 100 and/or the fuel nozzle 200 may be coupled to the endcover 32 via one or more conduits 50.

FIG. 4 provides a cross-sectioned perspective view of an exemplary nozzle segment 100 according to at least one embodiment of the present disclosure. As shown in FIG. 4, each nozzle segment 100 of the plurality of nozzle segments 100 includes a forward plate 102, an aft plate 104 that is axially offset from the forward plate 102 with respect to an axial centerline of the combustor 14 and an outer band 106 that at least partially defines a radially outer perimeter of the nozzle segment 100. The outer band 106 extends from the forward plate 102 to the aft plate 104. A fuel plenum 108 may be at least partially defined between the forward plate 102, the aft plate 104 and the outer band 106.

A plurality of tubes 110 extends through the forward plate 102, the fuel plenum 108 and the aft plate 104. Each tube 110 includes an inlet end or opening 112 disposed at or upstream from the forward plate 102 and an outlet end or opening 114 disposed downstream and/or extending axially away from the aft plate 104. In various embodiments one or more of the tubes 110 includes one or more fuel ports or holes 116 in fluid communication with the fuel plenum 108. Each tube 110 defines a passage or premix passage 118 through the respective nozzle segment 100. In operation, fuel may be supplied to the fuel plenum 108 via a corresponding fluid conduit 50. The fuel from the fuel plenum 108 may be injected into a respective premix passage 118 via fuel port(s) 116 where it is mixed with the compressed air 22 from the high pressure plenum 30. The fuel-air mixture is then injected from the respective tube 110 outlet 114 into the combustion chamber 36 where it is burned to produce the combustion gases 26.

In various embodiments, as shown in FIG. 4, the nozzle segment 100 includes an inlet flow conditioner 120. In particular embodiments, as shown in FIG. 4, the inlet flow conditioner 120 includes a sleeve 122 that is annularly shaped and that circumferentially surrounds a portion of fluid conduit 50. The sleeve 122 extends axially upstream from the forward plate 102. The sleeve 122 extends circumferentially around the respective inlets 112 to each respective tube 110 of the plurality of tubes 110. In particular embodiments, the sleeve 122 defines a plurality of apertures or holes 124 radially oriented and circumferentially spaced about the sleeve 122. In particular embodiments, the plurality of apertures 124 may be uniformly spaced or distributed or may be non-uniformly spaced or distributed along the sleeve 122. In particular embodiments, the plurality of apertures 124 may be uniformly sized or may be sized differently at various axial locations along the sleeve 122. In particular embodiments, the plurality of apertures 124 may be uniformly shaped or may have different shapes defined at various axial locations along the sleeve 122.

In particular embodiments, as shown in FIG. 4, the inlet flow conditioner 120 includes conditioner plate 126. In particular embodiments, the sleeve 122 extends from the conditioner plate 126 to the forward plate 102 of the nozzle segment 100. In particular embodiments, the conditioner plate 126 extends radially outwardly from and at least partially circumferentially around the fluid conduit 50. The conditioner plate 126, the sleeve 122 and the forward plate 102 at least partially define an inlet flow plenum 128 therebetween. The respective inlet 112 of each respective tube 110 is in fluid communication with the inlet flow plenum 128.

FIG. 5 provides a perspective view of an exemplary conditioner plate 126 according to at least one embodiment of the present disclosure. In particular embodiments, as shown in FIG. 5, the conditioner plate 126 may be wedge or pie shaped. As shown in FIG. 5, the conditioner plate 126 defines and/or includes a plurality of apertures 130. The plurality of apertures 130 is distributed across the conditioner plate 126. The flow area of the apertures 130 may be sized equally or may be sized differently with the flow area of some apertures 130 being smaller or larger than the flow area of other apertures 130. For example, in one embodiment a first aperture 130 of the plurality of apertures 130 may have a first diameter or flow area D1 and a second aperture 130 of the plurality of apertures 130 may have a second diameter or flow area D2 that is less than the first diameter D1.

Although the apertures 130 are illustrated in FIG. 5 as having a round shape, the particular shape of the apertures 130 is not limited to round or circular unless otherwise recited in the claims. For example, one or more of the apertures 130 may be oblong, square, rectangular, trapezoidal, triangular or have other shapes so as to have a desired effect on air flowing through the conditioner plate 126 into the inlet flow plenum 128.

FIG. 6 provides a cross-sectioned perspective view of an exemplary fuel nozzle 200 according to at least one embodiment of the present disclosure. As shown in FIG. 6, each fuel nozzle 200 includes a forward plate 202, an aft plate 204 that is axially offset from the forward plate 202 with respect to an axial centerline of the combustor 14 and an outer band 206 that at least partially defines a radially outer perimeter of the fuel nozzle 200. The outer band 206 extends from the forward plate 202 to the aft plate 204. A fuel plenum 208 may be at least partially defined between the forward plate 202, the aft plate 204 and the outer band 206.

A plurality of tubes 210 extends through the forward plate 202, the fuel plenum 208 and the aft plate 204. Each tube 210 includes an inlet end or opening 212 disposed at or upstream from the forward plate 202 and an outlet end or opening 214 disposed downstream and/or extending axially away from the aft plate 204. In various embodiments one or more of the tubes 210 includes one or more fuel ports or holes 216 in fluid communication with the fuel plenum 208. Each tube 210 defines a passage or premix passage 218 through the respective fuel nozzle 200.

In operation, fuel may be supplied to the fuel plenum 208 via a corresponding fluid conduit 50. The fuel from the fuel plenum 208 may be injected into a respective premix passage 218 via fuel port(s) 216 where it is mixed with the compressed air 22 from the high pressure plenum 30. The fuel-air mixture is then injected from the respective tube 210 outlet 214 into the combustion chamber 36 where it is burned to produce the combustion gases 26.

In various embodiments, as shown in FIG. 6, the fuel nozzle 200 includes an inlet flow conditioner 220. In particular embodiments, as shown in FIG. 6, the inlet flow conditioner 220 includes a sleeve 222 that is annularly shaped and that circumferentially surrounds a portion of fluid conduit 50. The sleeve 222 extends axially upstream from the forward plate 202. The sleeve 222 extends circumferentially around the respective inlet 212 to each respective tube 210 of the plurality of tubes 210. In particular embodiments, the sleeve 222 defines a plurality of apertures or holes 224 circumferentially spaced about the sleeve 222. In particular embodiments, the plurality of apertures 224 may be uniformly spaced or distributed or may be non-uniformly spaced or distributed along the sleeve 222. In particular embodiments, the plurality of apertures 224 may be uniformly sized or may be sized differently at various axial locations along the sleeve 222. In particular embodiments, the plurality of apertures 224 may be uniformly shaped or may have different shapes defined at various axial locations along the sleeve 222.

In particular embodiments, as shown in FIG. 6, the inlet flow conditioner 220 includes conditioner plate 226. In particular embodiments, the sleeve 222 extends from the conditioner plate 226 to the forward plate 202 of the fuel nozzle 200. In particular embodiments, the conditioner plate 226 extends radially outwardly from and at least partially circumferentially around the fluid conduit 50. The conditioner plate 226, the sleeve 222 and the forward plate 202 at least partially define an inlet flow plenum 228 therebetween. The respective inlet 212 of each respective tube 210 is in fluid communication with the inlet flow plenum 228.

FIG. 7 provides a perspective view of an exemplary conditioner plate 226 according to at least one embodiment of the present disclosure. As shown in FIG. 7, the conditioner plate 226 defines and/or includes a plurality of apertures 230. The plurality of apertures 230 is distributed across the conditioner plate 226. The flow area of the apertures 230 may be sized equally or may be sized differently with the flow area of some apertures 230 being smaller or larger than the flow area of other apertures 230. For example, in one embodiment a first aperture 230 of the plurality of apertures 230 may have a first diameter or flow area D1 and a second aperture 230 of the plurality of apertures 230 may have a second diameter or flow area D2 that is less than the first diameter D1

Although the apertures 230 are illustrated in FIG. 7 as having a round shape, the particular shape of the apertures 230 is not limited to round unless otherwise recited in the claims. For example, one or more of the apertures 230 may be oblong, square, rectangular, trapezoidal, triangular or have other shapes so as to have a desired effect on air flowing through the conditioner plate 226 into the inlet flow plenum 228.

During operation, as shown in FIGS. 2 through 7 collectively, compressed air 22 from the high pressure plenum 30 flows from the high pressure plenum towards the head end volume 46. A portion of the compressed air 22 may flow through apertures 124, 224 defined in the corresponding sleeve 122, 222 and into the corresponding flow distribution plenum 128, 228. A portion of the compressed air 22 then flows to the head end volume 46 where it reverses direction and flows through the corresponding apertures 130, 230 of the respective conditioning plate 126, 230.

The apertures 124, 224 reduce non-uniformity of the compressed air 22 as it enters the respective inlet flow plenums 128, 228 from the head end volume 46. The compressed air 22 having a substantially uniform flow field, enters the inlet(s) 112, 212 of the premix passage(s) 118, 218 in a substantially uniform fashion where fuel from the respective fuel plenums 108, 208 is injected into the flow of the compressed air 22 via the fuel ports 116, 216. The fuel and compressed air 22 mix within the respective premix passages 118, 218 and the mixture is then injected into the primary combustion chamber 36 where it is burned to produce combustion gases. The reduction in non-uniformity of the compressed air 22 provided by the respective conditioner plates 126, 226 as it enters the respective inlet flow plenums 128, 228 from the head end volume 46 improves mixing of the fuel and air within the premix passages 118, 218, thereby reducing overall NOx emissions of the combustor 14.

This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims. 

What is claimed is:
 1. A combustor, comprising: an inlet flow conditioner including a sleeve and a conditioner plate defining a plurality of apertures, wherein the sleeve extends axially from the conditioner plate to a forward plate of a nozzle segment, wherein the sleeve, the conditioner plate and the forward plate define an inlet flow plenum, and wherein the inlet flow plenum is in fluid communication with an inlet of a tube that defines a premix passage of the nozzle segment.
 2. The combustor as in claim 1, further comprising a head end volume at least partially defined between an endcover and the conditioner plate, wherein the inlet flow plenum is in fluid communication with the head end volume via the plurality of apertures.
 3. The combustor as in claim 1, wherein at least one aperture of the plurality of apertures is non-round.
 4. The combustor as in claim 1, where a first aperture of the plurality of apertures has a diameter that is less than a diameter of a second aperture of the plurality of apertures.
 5. The combustor as in claim 1, wherein the conditioner plate is wedge shaped.
 6. The combustor as in claim 1, wherein the sleeve defines a plurality of holes radially oriented and circumferentially spaced around the sleeve, wherein the plurality of holes provide for fluid communication into the inlet flow plenum.
 7. The combustor as in claim 1, further comprising a fluid conduit that extends axially through the conditioner plate, wherein the fluid conduit provides fuel to the premix passage.
 8. The combustor as in claim 1, wherein the nozzle segment further comprises an aft plate axially spaced from the forward plate, an outer band that extends between the forward plate and the aft plate, and a fuel plenum defined between the forward plate and the aft plate, wherein the tube extends through the forward plate, the fuel plenum and the aft plate.
 9. The combustor as in claim 7, wherein the tube is in fluid communication with the fuel plenum.
 10. A combustor, comprising: an inlet flow conditioner including a sleeve and a conditioner plate defining a plurality of apertures, wherein the sleeve extends axially from the conditioner plate to a forward plate of a fuel nozzle forming an inlet flow plenum therein, and wherein the inlet flow plenum is in fluid communication with a plurality of premix passages defined by a plurality of tubes of the fuel nozzle.
 11. The combustor as in claim 10, further comprising a head end volume at least partially defined between an endcover and the conditioner plate, wherein the inlet flow plenum is in fluid communication with the head end volume via the plurality of apertures.
 12. The combustor as in claim 10, wherein at least one aperture of the plurality of apertures is non-round.
 13. The combustor as in claim 10, where a first aperture of the plurality of apertures has a diameter that is less than a diameter of a second aperture of the plurality of apertures.
 14. The combustor as in claim 10, wherein the conditioner plate is circular shaped.
 15. The combustor as in claim 10, wherein the sleeve defines a plurality of holes radially oriented and circumferentially spaced around the sleeve, wherein the plurality of holes provide for fluid communication into the inlet flow plenum.
 16. The combustor as in claim 10, further comprising a fluid conduit that extends axially through the conditioner plate, wherein the fluid conduit provides fuel to the fuel nozzle and each premix passage of the plurality of premix passages.
 17. The combustor as in claim 10, wherein the fuel nozzle further comprises an aft plate axially spaced from the forward plate, an outer band that extends between the forward plate and the aft plate, and a fuel plenum defined between the forward plate and the aft plate, wherein the tube extends through the forward plate, the fuel plenum and the aft plate.
 18. The combustor as in claim 17, wherein each tube is in fluid communication with the fuel plenum.
 19. The combustor as in claim 10, further comparing a plurality of nozzle segments annularly arranged around the fuel nozzle, wherein each nozzle segment includes a sleeve and a conditioner plate defining a plurality of apertures, wherein the sleeve extends axially from the conditioner plate to a forward plate, wherein the sleeve, the conditioner plate and the forward plate define an inlet flow plenum, and wherein the inlet flow plenum is in fluid communication with a plurality of premix passages defined by a plurality of tubes of the nozzle segment. 